Euler solutions for a medium range cargo aircraft


Bahar C., Alemdaroǧlu N., ÖZYÖRÜK Y., Temel E.

40th AIAA Aerospace Sciences Meeting and Exhibit 2002, Reno, NV, United States Of America, 14 - 17 January 2002 identifier

  • Publication Type: Conference Paper / Full Text
  • Volume:
  • Doi Number: 10.2514/6.2002-402
  • City: Reno, NV
  • Country: United States Of America
  • Middle East Technical University Affiliated: Yes

Abstract

Inviscid, subsonic flow solutions for a medium range cargo aircraft were obtained at cruise and highlift configurations using the commercially available CFD-FASTRAN™ V2.2 code employing unstructured grid methodology. Calculations were performed for wing and aircraft configurations at various angles of attack. Preliminary calculations were done for a wing-alone case to determine the parameters of the grid generation and flow solution procedures. The wing studies with and without the engine nacelle showed that the addition of the nacelle disturbed the flow on the wing in the downstream region of the nacelle and as a result, the lift coefficient decreased at all angles of attack without a change in the lift curve slope, whereas the pitching moment was not affected significantly. Deployment of the flaps caused the aerodynamic coefficients to increase about one order of magnitude as expected in the high-lift configuration. The present results for the full aircraft computations showed that the lift coefficients varied linearly for cruise and high-lift configurations. Pitching moment coefficients showed characteristics of a stable aircraft. Since no experimental data on the investigated aircraft configuration were available in the open literature, the results were compared with the empirical results obtained by using the Advanced Aircraft Analysis (AAA) Software. Both results were observed to be in good agreement. © 2002 The American Institute of Aeronautics and Astronautics Inc. All rights reserved.